CN105197259A - Turnover type solar panel capable of unfolding towards light directionally - Google Patents
Turnover type solar panel capable of unfolding towards light directionally Download PDFInfo
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- CN105197259A CN105197259A CN201510692530.1A CN201510692530A CN105197259A CN 105197259 A CN105197259 A CN 105197259A CN 201510692530 A CN201510692530 A CN 201510692530A CN 105197259 A CN105197259 A CN 105197259A
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- solar panel
- transmission shaft
- solar energy
- satellite
- energy sailboard
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Abstract
The invention particularly relates to a turnover type solar panel capable of unfolding towards light directionally and solves the problems that the stability of the satellite is influenced, the working life is shortened and the solar panel is easy to damage because the conventional solar panel is unreasonable in structure. Grooves are formed in lateral edges of a satellite body; a solar panel body is arranged in each groove; a torsion spring is arranged between each solar panel body and the satellite body; each solar panel body comprises a strip-shaped frame; transmission shafts are arranged in each strip-shaped frame; memory alloy is arranged at the two ends of each transmission shaft; solar cell substrates are connected onto the memory alloy; a driving wheel is arranged on each transmission shaft; a driving belt is wound on the driving wheels; a driving motor is arranged in each strip-shaped frame; a worm and gear mechanism is arranged between the output shaft of each driving motor and the corresponding transmission shaft at any of the left end and the right end. According to the invention, the problem of failure of the whole solar panel because partial parts are damaged is avoided; meanwhile, the unfolding process is more stable.
Description
Technical field
The present invention relates to microsatellite to power with solar energy sailboard, be specially a kind of orientation and convertible solar energy sailboard is launched to light.
Background technology
The microsatellite of development both at home and abroad adopts solar panel to be directly attached to the design on microsatellite surface mostly at present.Although this design plan reduces microsatellite sum quality, occupy microsatellite major part celestial body face area, limit the lift-launch amount of microsatellite capacity weight, and the orientation that can not realize solar panel is to light action.Therefore, for microsatellite, while guarantee compact conformation, lightweight, solar energy sailboard provide sufficient electrical energy, carrying more capacity weights and realizing greater functionality is the importance studying microsatellite.
Conventional solar energy sailboard structure often exists that span is large, rigidity is low, structural damping is weak, the features such as coupling stiffness is lower between plate, and any one small disturbance all very easily evokes structural vibration.But, satellite is in operational process, multiple disturbing factor is inevitable, as external disturbance such as space debris, solar wind, thermal radiation, temperature shock, and the posture adjustment of satellite, become rail, internal disturbance that the limit cycles oscillations, the motion of spacecraft internal mechanism etc. of control system produce.There is not atmospheric damping in vacuum environment, said external interference or internal disturbance, once excite, carry out oneself's decay by being difficult to, dangerous self-evident, gently then affect the attitude stability of satellite, shorten work life; Heavy then directly damage solar energy sailboard mechanism, mechanism, once face global failure, cannot continue as celestial body and provide electric energy, and satellite also cannot normal operation.
When traditional solar energy sailboard launches, many employings torsion spring produces drive torque, in expansion process, resisting moment increases gradually with angle change, but drive torque but reduces thereupon, in order to ensure whole expansion process, certain moment nargin need be left, this has changed into mechanism's locking impact load with regard to making the remaining kinetic energy launching to end have no alternative but, and endangers more serious.
Summary of the invention
The present invention affect satellite stability to solve existing solar energy sailboard, shortens work life and the problem of fragile solar energy sailboard because unreasonable structure exists, provide a kind of compact conformation, lightweight, can realize directed to light, save satellite table area and the orientation that still can be continued power by other solar battery sheets after part solar battery sheet damages launch convertible solar energy sailboard to light.
The present invention adopts following technical scheme to realize: orientation launches convertible solar energy sailboard to light, comprise rectangular-shaped satellite body, the incline place of satellite body all has groove, be provided with hinged with satellite body in each groove and by the solar energy sailboard body that explosive bolt is connected, between solar energy sailboard body and satellite body, be provided with torsion spring; Solar energy sailboard body comprises strip framework, be provided with some in strip framework and pass its front-rear side walls and the transmission shaft be parallel to each other, the two ends of transmission shaft are provided with the memorial alloy hinged with it, memorial alloy is all connected with solar cell substrate, transmission shaft is provided with power wheel, power wheel is wound with the drive belt be close to it, be provided with drive motor in strip framework, between the output shaft of drive motor and the transmission shaft of left and right either end, be provided with the worm-and-wheel gear be connected with both.
When satellite arrives predetermined work track, control system lights explosive bolt, and four solar energy sailboard bodies, under torsion spring drives, eject in satelloid, after solar energy sailboard body ejects completely, control system excites memorial alloy, solar cell substrate is launched, after solar cell substrate is deployed into assigned address, control system in satellite main body sends instruction, starter motor, transmission shaft drives power wheel and drive belt to rotate, and then drives each transmission shaft and solar cell substrate to rotate, optical sensor on solar cell substrate by induction by most intense light irradiation induction angle feed-back to the control system of inside satellite, the motor rotations reaching this angle and need is calculated again by control system, output signal controls electric machine rotation, each solar cell substrate is driven to rotate by drive belt, the orientation realizing solar cell substrate adjusts light, thus make solar cell substrate accept maximum illuminating area, improve illumination degree of utilization, overcome existing solar energy sailboard and affect satellite stability because unreasonable structure exists, shorten work life and the problem of fragile solar energy sailboard.
The end of transmission shaft is installed with bearing pin, and bearing pin is installed with memorial alloy, and the side, bottom of memorial alloy is convex structure, and is close to strip framework sidewall.
In order to prevent cell panel from launching excessively, after solar cell substrate turns to memorial alloy base plane and strip framework sidewall is close to, memorial alloy realizes spacing.
Reasonable in design of the present invention is reliable, volume is little, quality is light, be placed in satelloid, save celestial body face area, so that Seeds of First Post-flight more multi-load, satellite is made to realize more function, and the structure of multi-disc solar cell substrate, avoid solar cell substrate because of the external interference such as space debris, solar wind, the problem making mechanism only because a part of failsafety but cause whole solar energy sailboard to paralyse; Solar energy sailboard expansion process is more steady simultaneously, avoids the problem of greater impact load.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is the structural representation of solar energy sailboard body in Fig. 1;
Fig. 3 is the structural representation at memorial alloy place in Fig. 1.
In figure: 1-satellite body, 2-groove, 3-solar energy sailboard body, 4-strip framework, 5-transmission shaft, 6-memorial alloy, 7-solar cell substrate, 8-power wheel, 9-drive belt, 10-drive motor, 11-worm-and-wheel gear, 12-bearing pin.
Detailed description of the invention
Orientation launches convertible solar energy sailboard to light, comprise rectangular-shaped satellite body 1, the incline place of satellite body 1 all has groove 2, be provided with hinged with satellite body 1 in each groove 2 and by the solar energy sailboard body 3 that explosive bolt is connected, between solar energy sailboard body 3 and satellite body 1, be provided with torsion spring; Solar energy sailboard body 3 comprises strip framework 4, be provided with some in strip framework 4 and pass its front-rear side walls and the transmission shaft 5 be parallel to each other, the two ends of transmission shaft 5 are provided with the memorial alloy 6 hinged with it, memorial alloy 6 is all connected with solar cell substrate 7, transmission shaft 5 is provided with power wheel 8, power wheel 8 is wound with the drive belt 9 be close to it, be provided with drive motor 10 in strip framework 4, between the output shaft of drive motor 10 and the transmission shaft 5 of left and right either end, be provided with the worm-and-wheel gear 11 be connected with both.
The end of transmission shaft 5 is installed with bearing pin 12, bearing pin 12 is installed with memorial alloy 6, and the side, bottom of memorial alloy 6 is convex structure, and is close to strip framework sidewall.
In specific implementation process, satellite body 1 is of a size of 320mm × 320mm × 700mm; Memorial alloy 6 is super-elasticity Ultimum Ti.
Claims (2)
1. an orientation launches convertible solar energy sailboard to light, it is characterized in that: comprise rectangular-shaped satellite body (1), the incline place of satellite body (1) all has groove (2), be provided with hinged with satellite body (1) in each groove (2) and by the solar energy sailboard body (3) that explosive bolt is connected, between solar energy sailboard body (3) and satellite body (1), be provided with torsion spring, solar energy sailboard body (3) comprises strip framework (4), be provided with some in strip framework (4) and pass its front-rear side walls and the transmission shaft be parallel to each other (5), the two ends of transmission shaft (5) are provided with the memorial alloy (6) hinged with it, memorial alloy (6) is all connected with solar cell substrate (7), transmission shaft (5) is provided with power wheel (8), power wheel (8) is wound with the drive belt (9) be close to it, drive motor (10) is provided with in strip framework (4), the worm-and-wheel gear (11) be connected with both is provided with between the output shaft of drive motor (10) and the transmission shaft (5) of left and right either end.
2. orientation according to claim 1 launches convertible solar energy sailboard to light, it is characterized in that: the end of transmission shaft (5) is installed with bearing pin (12), bearing pin (12) is installed with memorial alloy (6), the side, bottom of memorial alloy (6) is convex structure, and is close to strip framework sidewall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510692530.1A CN105197259B (en) | 2015-10-23 | 2015-10-23 | Turnover type solar panel capable of unfolding towards light directionally |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510692530.1A CN105197259B (en) | 2015-10-23 | 2015-10-23 | Turnover type solar panel capable of unfolding towards light directionally |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105197259A true CN105197259A (en) | 2015-12-30 |
| CN105197259B CN105197259B (en) | 2017-04-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510692530.1A Expired - Fee Related CN105197259B (en) | 2015-10-23 | 2015-10-23 | Turnover type solar panel capable of unfolding towards light directionally |
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| CN (1) | CN105197259B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742084A (en) * | 2016-11-23 | 2017-05-31 | 上海卫星工程研究所 | It is a kind of to be applied to the eight prism support meanss that 15 antennas are uniformly installed |
| CN107954005A (en) * | 2017-12-21 | 2018-04-24 | 星际漫步（北京）航天科技有限公司 | Telescopic mechanism for outspreading sailboard of solar cell and method of deploying |
| CN109484673A (en) * | 2018-12-24 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of payload platform separate type remote sensing micro satellite configuration and its assembly method |
| CN110641741A (en) * | 2019-10-23 | 2020-01-03 | 北京国电高科科技有限公司 | Double-freedom-degree solar panel control method and control system thereof |
| CN112009725A (en) * | 2020-09-02 | 2020-12-01 | 中国电子科技集团公司第十八研究所 | Memory alloy space solar wing unfolding device |
| CN117154372A (en) * | 2023-10-31 | 2023-12-01 | 银河航天科技(南通)有限公司 | Satellite turns over board expansion device with angle modulation |
Citations (4)
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| CN1204604A (en) * | 1997-07-05 | 1999-01-13 | 戴姆勒－奔驰航空公司 | Transmission for moving baseplate fitted with solar cell on spacecraft |
| CN2815880Y (en) * | 2005-06-01 | 2006-09-13 | 梁锡昌 | Solar-cell sailboard straightening and positioning mechanism |
| CN101372995A (en) * | 2008-09-19 | 2009-02-25 | 航天东方红卫星有限公司 | Memory alloy automatic locking device of movable brace rod |
| CN102324438A (en) * | 2011-08-18 | 2012-01-18 | 哈尔滨工业大学 | Inflation expansion truss solar panel array capable of on-orbit assembly |
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2015
- 2015-10-23 CN CN201510692530.1A patent/CN105197259B/en not_active Expired - Fee Related
Patent Citations (4)
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| CN1204604A (en) * | 1997-07-05 | 1999-01-13 | 戴姆勒－奔驰航空公司 | Transmission for moving baseplate fitted with solar cell on spacecraft |
| CN2815880Y (en) * | 2005-06-01 | 2006-09-13 | 梁锡昌 | Solar-cell sailboard straightening and positioning mechanism |
| CN101372995A (en) * | 2008-09-19 | 2009-02-25 | 航天东方红卫星有限公司 | Memory alloy automatic locking device of movable brace rod |
| CN102324438A (en) * | 2011-08-18 | 2012-01-18 | 哈尔滨工业大学 | Inflation expansion truss solar panel array capable of on-orbit assembly |
Non-Patent Citations (1)
| Title |
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| 谢宗武: "空间太阳能电池阵列技术综述", 《宇航学报》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742084A (en) * | 2016-11-23 | 2017-05-31 | 上海卫星工程研究所 | It is a kind of to be applied to the eight prism support meanss that 15 antennas are uniformly installed |
| CN106742084B (en) * | 2016-11-23 | 2019-08-02 | 上海卫星工程研究所 | A kind of eight prism support devices uniformly installed suitable for 15 antennas |
| CN107954005A (en) * | 2017-12-21 | 2018-04-24 | 星际漫步（北京）航天科技有限公司 | Telescopic mechanism for outspreading sailboard of solar cell and method of deploying |
| CN107954005B (en) * | 2017-12-21 | 2024-01-30 | 星际漫步（北京）航天科技有限公司 | Expansion mechanism and expansion method for telescopic solar cell sailboard |
| CN109484673A (en) * | 2018-12-24 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of payload platform separate type remote sensing micro satellite configuration and its assembly method |
| CN110641741A (en) * | 2019-10-23 | 2020-01-03 | 北京国电高科科技有限公司 | Double-freedom-degree solar panel control method and control system thereof |
| CN112009725A (en) * | 2020-09-02 | 2020-12-01 | 中国电子科技集团公司第十八研究所 | Memory alloy space solar wing unfolding device |
| CN117154372A (en) * | 2023-10-31 | 2023-12-01 | 银河航天科技(南通)有限公司 | Satellite turns over board expansion device with angle modulation |
| CN117154372B (en) * | 2023-10-31 | 2024-01-02 | 银河航天科技(南通)有限公司 | Satellite turns over board expansion device with angle modulation |
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| CN105197259B (en) | 2017-04-12 |
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